US4004755A - VTOL aircraft with combined air brake and deflector door - Google Patents

VTOL aircraft with combined air brake and deflector door Download PDF

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Publication number
US4004755A
US4004755A US05/600,305 US60030575A US4004755A US 4004755 A US4004755 A US 4004755A US 60030575 A US60030575 A US 60030575A US 4004755 A US4004755 A US 4004755A
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US
United States
Prior art keywords
door
air
aircraft
blowing
fuselage
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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US05/600,305
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English (en)
Inventor
Ralph Spenser Hooper
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BAE Systems PLC
Original Assignee
Hawker Siddeley Aviation Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hawker Siddeley Aviation Ltd filed Critical Hawker Siddeley Aviation Ltd
Application granted granted Critical
Publication of US4004755A publication Critical patent/US4004755A/en
Assigned to BRITISH AEROSPACE PUBLIC LIMITED COMPANY reassignment BRITISH AEROSPACE PUBLIC LIMITED COMPANY CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). EFFECTIVE JAN. 2, 1981 Assignors: BRITISH AEROSPACE LIMITED
Assigned to BRITISH AEROSPACE reassignment BRITISH AEROSPACE ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: HAWKER SIDDELEY AVIATION LIMITED
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
    • B64C29/005—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors the motors being fixed relative to the fuselage

Definitions

  • a hot gas deflector door incorporating edgewise air blowing means and movably mounted on the underside of the aircraft fuselage such that it is movable from a retracted position, in which it may conform to the fuselage profile, to a fully open position in which it is directed forwardly and downwardly.
  • this deflector door influences the forward moving component of the efflux gas ⁇ fountain ⁇ flow, deflecting it in a downward direction such that it will tend to re-attach itself to the forwardly directed horizontal ground surface gas flow sheet emanating from the impingement of the nozzle flow with the ground.
  • This effect is enhanced by the sheet of blown air emanating from the lower edge of the door, which blown air will, in addition, ensure clean flow separation from the door edge, instead of the vortex pattern resulting from a non-blown door which could still result in low energy hot gas in the vicinity of the air intake.
  • the blowing air is, for preference, obtained as a supply of bleed air from the engine. Although it has previously been indicated that such a source of supply is uneconomical and possibly detrimental to engine performance, the flow rate in the present instance will be minimised due to the proximity of the blowing edge to the ground. It may be preferable to arrange a gradation of blowing intensity and/or direction of flow along the edges of the door to suit the particular installation, with the objective of economising in bleed flow.
  • the angular direction of blowing envisaged above may include angles within the plane of the door or within a plane transverse, e.g. normal, to it.
  • the door itself may be shaped (rather than flat as illustrated in the accompanying drawings) to suit any particular installation and in order to direct or concentrate the hot air flow away from the vicinity of the air intakes.
  • the door serves both as a deflector door and an air brake, the door being capable of being opened by selected amounts depending on braking requirements, although means may be provided to ensure that blowing air is automatically supplied to the door only when the door engine nozzles are turned downwards to typically 60° or more from the horizontal and the deflector door is deployed substantially in its fully opened position.
  • FIG. 1 is a side elevation of an aircraft of the vectored thrust type fitted with deflector means according to the invention
  • FIG. 2 is an end elevation looking on the forward end of the same aircraft
  • FIG. 3 is a plan view
  • FIG. 4 is a detail side elevation in the vicinity of the deflector door, with the door shown in its fully open attitude
  • FIG. 5 is a front elevation in the direction of the arrow 5 of FIG. 4;
  • FIG. 6 is an inverted plan view, in the direction of the arrow 6 of FIG. 4, depicting the door construction and its relationship to the fuselage structure when closed;
  • FIG. 7 is a detail section taken on the line 7 -- 7 of FIG. 4 depicting the bleed air supply to the door structure.
  • FIG. 8 is a section taken on the line 8 -- 8 of FIG. 6 showing the blowing slot of the door.
  • FIGS. 1 and 2 of the drawings an aircraft is shown with forward and rear pairs of propulsive nozzles 1 and 2 rotated downward to produce a lifting thrust on the aircraft.
  • the forward and larger nozzles 1 supplied with air bled from the engine compressor, incorporate plenum chamber burning as previously described, while the rear nozzle effluxes derive from the engine turbine.
  • Gas flow impingement with the ground and the several resultant flow components are indicated by the arrows 3 of FIGS. 1 and 3, from which it will be seen that some of the spreading gas will meet in a central region between the nozzles and rise towards the fuselage and thence disperse. This is referred to as ⁇ fountain ⁇ flow.
  • the forward moving component 4 of the rising gas stream is deflected obliquely downwards and forwards by a combined airbrake/ deflector door 5 hinged on the fuselage at 6 and movable by means of an operating jack 10 (FIG. 4) from a retracted rearward position 8, where it lies flush and forms part of the fuselage profile, to the fully open attitude as shown.
  • the door 5 incorporates blowing means, the forward movement of the ⁇ fountain ⁇ flow being further influenced by the emission of blowing air 9 (FIGS. 1 and 5) from edgewise blowing slots 7 supplied through a duct 11 from the engine compressor.
  • the blowing air 9 in addition to its emission from the lower edge 21 of the door 5, also issues from the slightly converging lower side portions 22 giving a degree of fanwise spread, the blowing slots being differently oriented, principally as a consequence of the profile of the lower part of the door 5, so that the direction of air blowing varies along the door edge to achieve the desired spread as indicated by the arrows in FIG. 5.
  • the forward component of the hot gas flow 4 in direct fore and aft line with the door influenced to reattach to the ground surface gas flow 3a but partially laterally dispersed flow moving in a forward direction may also come under the influence of the blowing air.
  • the lower edge of the door needs to be high enough to allow for a burst tyre or collapsed oleo leg condition.
  • the bleed air supply duct 11 is located on the aircraft longitudinal centre line and terminates at its forward end in a short length of transverse ducting 12 concentrically disposed about the door hinge line 6.
  • the short transverse duct length 12 lies in a recess in the portion of the door through which the hinge line 6 passes and the ends of this duct 12 terminate close to apertures in longitudinal diaphragms 13 of the door forming the boundaries of the recess.
  • Each diaphragm 13 has an attached housing 14 received in an inner bearing 15 for the door on the fuselage fixed structure, which bearing surrounds the duct 12.
  • the door incorporates outer longitudinal edge panels 16 which are provided with spigots 17 received in outer bearings 17a on the fixed fuselage structure.
  • the ends of the duct 12 are a rotary fit within the bores of the housings 14 and are provided with sealing rings 18 which permit relative rotation of the door and duct but prevent escape of the bleed air.
  • the air leaving the ends of the duct 12 passes through the holes in the diaphragms 13 into a pair of curved ducts 19 in the interior of the door.
  • These ducts supply two chambers 20 in the door from which the air is emitted through the blowing slots 7.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Tents Or Canopies (AREA)
  • Emergency Lowering Means (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Looms (AREA)
US05/600,305 1974-08-06 1975-07-30 VTOL aircraft with combined air brake and deflector door Expired - Lifetime US4004755A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB34680/74A GB1512645A (en) 1974-08-06 1974-08-06 Aircraft
UK34680/74 1974-08-06

Publications (1)

Publication Number Publication Date
US4004755A true US4004755A (en) 1977-01-25

Family

ID=10368642

Family Applications (1)

Application Number Title Priority Date Filing Date
US05/600,305 Expired - Lifetime US4004755A (en) 1974-08-06 1975-07-30 VTOL aircraft with combined air brake and deflector door

Country Status (3)

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US (1) US4004755A (enrdf_load_stackoverflow)
DE (1) DE2535511A1 (enrdf_load_stackoverflow)
GB (1) GB1512645A (enrdf_load_stackoverflow)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4506848A (en) * 1980-12-22 1985-03-26 British Aerospace Public Limited Company Aircraft configuration and control arrangement therefor
US5779169A (en) * 1995-12-15 1998-07-14 The Boeing Company Aircraft engine inlet hot gas and foreign object ingestion reduction and pitch control system
JP2948325B2 (ja) 1990-12-04 1999-09-13 三菱重工業株式会社 航空機
WO2000020272A1 (en) * 1998-10-06 2000-04-13 Northrop Grumman Corporation Aircraft engine air intake system
US6371407B1 (en) * 2000-07-05 2002-04-16 Lockheed Martin Corporation Mechanism for vectoring exhaust flow
US20030033798A1 (en) * 2001-08-17 2003-02-20 Dickau John Eugene VTOL aircraft propulsion systems and forward flight thrust vectoring
US20070018034A1 (en) * 2005-07-12 2007-01-25 Dickau John E Thrust vectoring
US20090242698A1 (en) * 2008-03-31 2009-10-01 Honda Motor Co., Ltd. Aerodynamic braking device for aircraft
US8167249B1 (en) 2009-03-25 2012-05-01 The Boeing Company Controllable upper surface blown nozzle
US8302908B1 (en) 2009-03-25 2012-11-06 The Boeing Company Blended wing aircraft
US8317129B1 (en) * 2009-03-25 2012-11-27 The Boeing Company Universal convergent nozzle and distinct nozzle aperture
US8322655B1 (en) 2009-03-25 2012-12-04 The Boeing Company Twin-boom empennage
US8382045B2 (en) 2009-07-21 2013-02-26 The Boeing Company Shape-changing control surface
US8403256B1 (en) 2009-03-25 2013-03-26 The Boeing Company Swept-wing powered-lift aircraft
KR101871628B1 (ko) * 2017-03-03 2018-06-27 인하대학교 산학협력단 이동식방열판

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3542541A1 (de) * 1985-12-02 1987-06-04 Ingelheim Peter Graf Von Vorrichtung zur erzeugung einer vortriebskraft

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3073548A (en) * 1960-01-22 1963-01-15 Hawker Aircraft Ltd Vtol aircraft with gas diversion means
US3447764A (en) * 1966-05-21 1969-06-03 Bristol Siddeley Engines Ltd Aircraft with jet propulsion engine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3073548A (en) * 1960-01-22 1963-01-15 Hawker Aircraft Ltd Vtol aircraft with gas diversion means
US3447764A (en) * 1966-05-21 1969-06-03 Bristol Siddeley Engines Ltd Aircraft with jet propulsion engine

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4506848A (en) * 1980-12-22 1985-03-26 British Aerospace Public Limited Company Aircraft configuration and control arrangement therefor
JP2948325B2 (ja) 1990-12-04 1999-09-13 三菱重工業株式会社 航空機
US5779169A (en) * 1995-12-15 1998-07-14 The Boeing Company Aircraft engine inlet hot gas and foreign object ingestion reduction and pitch control system
WO2000020272A1 (en) * 1998-10-06 2000-04-13 Northrop Grumman Corporation Aircraft engine air intake system
US6371407B1 (en) * 2000-07-05 2002-04-16 Lockheed Martin Corporation Mechanism for vectoring exhaust flow
US20030033798A1 (en) * 2001-08-17 2003-02-20 Dickau John Eugene VTOL aircraft propulsion systems and forward flight thrust vectoring
US6918244B2 (en) * 2001-08-17 2005-07-19 John Eugene Dickau Vertical takeoff and landing aircraft propulsion systems
US20060027704A1 (en) * 2001-08-17 2006-02-09 Dickau John E Internal duct VTOL aircraft propulsion system
US20070018034A1 (en) * 2005-07-12 2007-01-25 Dickau John E Thrust vectoring
US8231079B2 (en) 2008-03-31 2012-07-31 Honda Patents & Technologies North America, Llc Aerodynamic braking device for aircraft
US20090242698A1 (en) * 2008-03-31 2009-10-01 Honda Motor Co., Ltd. Aerodynamic braking device for aircraft
US8167249B1 (en) 2009-03-25 2012-05-01 The Boeing Company Controllable upper surface blown nozzle
US8302908B1 (en) 2009-03-25 2012-11-06 The Boeing Company Blended wing aircraft
US8317129B1 (en) * 2009-03-25 2012-11-27 The Boeing Company Universal convergent nozzle and distinct nozzle aperture
US8322655B1 (en) 2009-03-25 2012-12-04 The Boeing Company Twin-boom empennage
US8353478B1 (en) 2009-03-25 2013-01-15 The Boeing Company Blended wing aircraft
US8403256B1 (en) 2009-03-25 2013-03-26 The Boeing Company Swept-wing powered-lift aircraft
US8567711B1 (en) 2009-03-25 2013-10-29 The Boeing Company Swept-wing powered-lift aircraft
US8720817B1 (en) 2009-03-25 2014-05-13 The Boeing Company Twin-boom empennage
US8382045B2 (en) 2009-07-21 2013-02-26 The Boeing Company Shape-changing control surface
KR101871628B1 (ko) * 2017-03-03 2018-06-27 인하대학교 산학협력단 이동식방열판

Also Published As

Publication number Publication date
DE2535511C2 (enrdf_load_stackoverflow) 1987-09-03
DE2535511A1 (de) 1976-07-01
GB1512645A (en) 1978-06-01

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AS Assignment

Owner name: BRITISH AEROSPACE PUBLIC LIMITED COMPANY

Free format text: CHANGE OF NAME;ASSIGNOR:BRITISH AEROSPACE LIMITED;REEL/FRAME:004080/0820

Effective date: 19820106

Owner name: BRITISH AEROSPACE PUBLIC LIMITED COMPANY, DISTRICT

Free format text: CHANGE OF NAME;ASSIGNOR:BRITISH AEROSPACE LIMITED;REEL/FRAME:004080/0820

Effective date: 19820106

AS Assignment

Owner name: BRITISH AEROSPACE, BROOKLANDS RD., WEYBRIDGE SURRE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST. AS OF APR. 17,1978;ASSIGNOR:HAWKER SIDDELEY AVIATION LIMITED;REEL/FRAME:003953/0751

Effective date: 19811218

Owner name: BRITISH AEROSPACE, ENGLAND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:HAWKER SIDDELEY AVIATION LIMITED;REEL/FRAME:003953/0751

Effective date: 19811218